轴流压气机主流在封严篦齿上游容腔内流动结构的数值研究  

Numerical Simulation Research of Flow Structure of Axial Compressor Mainstream in Upstream Cavity

作　　者：傅鑫[1] 王婉月 张衍 朱超 Fu Xin;Wang Wanyue;Zhang Yan;Zhu Chao(College of Energy&Power Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China;China South Industries Group Research Institute,Beijing 100089,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国南方工业研究院,北京100089

出　　处：《兵工自动化》2018年第7期83-88,共6页Ordnance Industry Automation

基　　金：航空推进技术验证计划项目(APTD-0302-01)

摘　　要：为了解燃气轮机压气机静子上游容腔二次流结构以及提高效率,利用3维数值模拟方法对带有封严结构的压气机上游空腔内的流动结构和产生的气动损失进行分析,给定0.5%和1.0%的间隙叶高比,并研究主流在上游容腔结构内产生的二次流与泄漏流的相互作用。静子通道内的二次流除了通过封严篦齿的泄漏流外,主流会在上游容腔内产生与泄漏流类似的与主流流向差异较大的二次流。分析结果表明:间隙叶高比为0.5%与间隙叶高比为1.0%相比,泄漏量减少53%的同时损失系数只降低1.784%,主流在上游容腔内会产生较多的二次流,而间隙叶高比为1.0%的情况下泄漏量增加,主流在上游容腔结构内产生的二次流效应减弱。Three-dimensional numerical simulations have been performed to investigate the flow structure of the upstream cavity and the aerodynamic loss in a compressor cascade with labyrinth seal.On the basis of this analysis,the interaction of the secondary flow generated by upstream cavity and the leakage flow was studied.In addition to the classical hub secondary flow that caught by labyrinth seal,another secondary flow was found which is similar to leakage flow and generated by the mainstream in the upstream cavity.Detailed analyses of the interaction of the upstream cavity secondary flow and the leakage flow reveals:when the percent of seal-clearance/blade span ratio decreases from 1.0%to 0.5%,the mass of leakage flow decreases by 53%and the aerodynamic loss only decreases by 1.784%.With 0.5%seal clearance ratio,the upstream cavity creates more secondary flow.With increasing seal clearance ratio,the secondary flow effect generated by upstream cavity is weaken.

关 键 词：航空宇航推进理论及工程 封严篦齿 上游容腔 泄漏流 二次流 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]